Pusher turboprop powerplant installation

A turboprop gas turbine engine adapted to be mounted to an aircraft, the turboprop gas turbine engine comprising:

• an engine core and a gearbox driving a propeller, the engine core and the gearbox being enclosed within a nacelle, the propeller located rearward of the gearbox and the engine core relative to a direction of travel of the aircraft, the turboprop gas turbine engine being a pusher engine;
• an air intake disposed within the nacelle and formed to direct ambient air into the engine core of the turboprop gas turbine engine, the air intake including an air inlet duct having a forward-facing intake inlet receiving the ambient air, the air inlet duct including an upstream section and a downstream section, the upstream section of the air inlet duct in fluid communication with the intake inlet and extending downstream from the intake inlet, the downstream section of the air inlet duct fluidly connected to and directing air from the upstream section into an engine air inlet of the engine core, and a second air outlet duct located within the nacelle, the second air outlet duct directing air into an air-cooled-oil-cooler (ACOC);
• and
• an inertial particle separator (IPS) located downstream of the intake inlet and upstream of the engine air inlet, the inertial particle separator operable to redirect FOD particles in the air flowing through the air inlet duct into an IPS duct connected in fluid flow communication with the air inlet duct, the ACOC and the IPS being integrated into a common duct located axially forward of the engine core.